EP1426558A3 - Gas turbine transition piece with dimpled surface and cooling method for such a transition piece - Google Patents

Gas turbine transition piece with dimpled surface and cooling method for such a transition piece Download PDF

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Publication number
EP1426558A3
EP1426558A3 EP03257323A EP03257323A EP1426558A3 EP 1426558 A3 EP1426558 A3 EP 1426558A3 EP 03257323 A EP03257323 A EP 03257323A EP 03257323 A EP03257323 A EP 03257323A EP 1426558 A3 EP1426558 A3 EP 1426558A3
Authority
EP
European Patent Office
Prior art keywords
transition piece
gas turbine
cooling method
dimpled surface
plenum
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP03257323A
Other languages
German (de)
French (fr)
Other versions
EP1426558A2 (en
Inventor
Ronald Scott Bunker
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP1426558A2 publication Critical patent/EP1426558A2/en
Publication of EP1426558A3 publication Critical patent/EP1426558A3/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A transition piece assembly (42) for a gas turbine includes a transition piece (44) having one end adapted for connection to a gas turbine combustor and an opposite end adapted for connection to a first turbine stage; the transition piece has an exterior surface formed with a plurality of concave dimples (48) thereon. An impingement flow sleeve (46) surrounds the transition piece, establishing a plenum (54) therebetween. The impingement sleeve is formed with a plurality of cooling apertures (52) therein for introducing compressor cooling air into the plenum.
EP03257323A 2002-11-22 2003-11-19 Gas turbine transition piece with dimpled surface and cooling method for such a transition piece Withdrawn EP1426558A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US301672 1981-09-14
US30167202A 2002-11-22 2002-11-22

Publications (2)

Publication Number Publication Date
EP1426558A2 EP1426558A2 (en) 2004-06-09
EP1426558A3 true EP1426558A3 (en) 2005-02-09

Family

ID=32312171

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03257323A Withdrawn EP1426558A3 (en) 2002-11-22 2003-11-19 Gas turbine transition piece with dimpled surface and cooling method for such a transition piece

Country Status (3)

Country Link
EP (1) EP1426558A3 (en)
JP (1) JP2004177109A (en)
KR (1) KR20040045359A (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7082766B1 (en) * 2005-03-02 2006-08-01 General Electric Company One-piece can combustor
US7886991B2 (en) * 2008-10-03 2011-02-15 General Electric Company Premixed direct injection nozzle
US8051662B2 (en) * 2009-02-10 2011-11-08 United Technologies Corp. Transition duct assemblies and gas turbine engine systems involving such assemblies
US20100205972A1 (en) * 2009-02-17 2010-08-19 General Electric Company One-piece can combustor with heat transfer surface enhacements
US8438856B2 (en) * 2009-03-02 2013-05-14 General Electric Company Effusion cooled one-piece can combustor
US8695322B2 (en) * 2009-03-30 2014-04-15 General Electric Company Thermally decoupled can-annular transition piece
JP2012145098A (en) 2010-12-21 2012-08-02 Toshiba Corp Transition piece, and gas turbine
US20120324898A1 (en) * 2011-06-21 2012-12-27 Mcmahan Kevin Weston Combustor assembly for use in a turbine engine and methods of assembling same
US8915087B2 (en) * 2011-06-21 2014-12-23 General Electric Company Methods and systems for transferring heat from a transition nozzle
US20130086920A1 (en) * 2011-10-05 2013-04-11 General Electric Company Combustor and method for supplying flow to a combustor
US9145778B2 (en) * 2012-04-03 2015-09-29 General Electric Company Combustor with non-circular head end
EP2960436B1 (en) 2014-06-27 2017-08-09 Ansaldo Energia Switzerland AG Cooling structure for a transition piece of a gas turbine
US9976487B2 (en) * 2015-12-22 2018-05-22 General Electric Company Staged fuel and air injection in combustion systems of gas turbines
WO2018021993A1 (en) * 2016-07-25 2018-02-01 Siemens Aktiengesellschaft Cooling features for a gas turbine engine
KR102164620B1 (en) 2019-06-19 2020-10-12 두산중공업 주식회사 Combustor and gas turbine including the same
CN113091091A (en) * 2021-05-13 2021-07-09 中国联合重型燃气轮机技术有限公司 Combustion chamber laminate and combustion chamber

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1410137A (en) * 1973-11-02 1975-10-15 Avco Corp Gas turbine engines
US5802841A (en) * 1995-11-30 1998-09-08 Kabushiki Kaisha Toshiba Gas turbine cooling system
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
EP1143107A2 (en) * 2000-04-06 2001-10-10 General Electric Company Gas turbine transition duct end frame cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1410137A (en) * 1973-11-02 1975-10-15 Avco Corp Gas turbine engines
US5802841A (en) * 1995-11-30 1998-09-08 Kabushiki Kaisha Toshiba Gas turbine cooling system
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
EP1143107A2 (en) * 2000-04-06 2001-10-10 General Electric Company Gas turbine transition duct end frame cooling

Also Published As

Publication number Publication date
KR20040045359A (en) 2004-06-01
EP1426558A2 (en) 2004-06-09
JP2004177109A (en) 2004-06-24

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